US5363768A - Propellant gas-generation system for canister ejection - Google Patents

Propellant gas-generation system for canister ejection Download PDF

Info

Publication number
US5363768A
US5363768A US07/679,305 US67930591A US5363768A US 5363768 A US5363768 A US 5363768A US 67930591 A US67930591 A US 67930591A US 5363768 A US5363768 A US 5363768A
Authority
US
United States
Prior art keywords
propellant
strip
substrate
adhesive
canister
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US07/679,305
Other languages
English (en)
Inventor
Mark A. Solberg
James A. Hartwell
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Northrop Grumman Innovation Systems LLC
Original Assignee
Thiokol Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Thiokol Corp filed Critical Thiokol Corp
Priority to US07/679,305 priority Critical patent/US5363768A/en
Assigned to THIOKOL CORPORATION, 2475 WASHINGTON BLVD., OGDEN, UT 84405, A DE CORP. reassignment THIOKOL CORPORATION, 2475 WASHINGTON BLVD., OGDEN, UT 84405, A DE CORP. ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: HARTWELL, JAMES A., SOLBERG, MARK A.
Priority to GB9205951A priority patent/GB2307031B/en
Priority to FR9203940A priority patent/FR2737288A1/fr
Priority to US07/911,941 priority patent/US5616884A/en
Application granted granted Critical
Publication of US5363768A publication Critical patent/US5363768A/en
Assigned to CORDANT TECHNOLOGIES, INC. reassignment CORDANT TECHNOLOGIES, INC. CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: THIOKOL CORPORATION
Assigned to THE CHASE MANHATTAN BANK reassignment THE CHASE MANHATTAN BANK PATENT SECURITY AGREEMENT Assignors: ALLIANT TECHSYSTEMS INC.
Assigned to ALLIANT TECHSYSTEMS INC. reassignment ALLIANT TECHSYSTEMS INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: THIOKOL PROPULSION CORP.
Assigned to THIOKOL PROPULSION CORP. reassignment THIOKOL PROPULSION CORP. CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: CORDANT TECHNOLOGIES INC.
Assigned to ALLIANT TECHSYSTEMS INC. reassignment ALLIANT TECHSYSTEMS INC. RELEASE OF SECURITY AGREEMENT Assignors: JPMORGAN CHASE BANK (FORMERLY KNOWN AS THE CHASE MANHATTAN BANK)
Assigned to BANK OF AMERICA, N.A. reassignment BANK OF AMERICA, N.A. SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ALLANT AMMUNITION AND POWDER COMPANY LLC, ALLIANT AMMUNITION SYSTEMS COMPANY LLC, ALLIANT HOLDINGS LLC, ALLIANT INTERNATIONAL HOLDINGS INC., ALLIANT LAKE CITY SMALL CALIBER AMMUNTION COMPANY LLC, ALLIANT SOUTHERN COMPOSITES COMPANY LLC, ALLIANT TECHSYSTEMS INC., AMMUNITION ACCESSORIES INC., ATK AEROSPACE COMPANY INC., ATK AMMUNITION AND RELATED PRODUCTS LLC, ATK COMMERCIAL AMMUNITION COMPANY INC., ATK ELKTON LLC, ATK LOGISTICS AND TECHNICAL SERVICES LLC, ATK MISSILE SYSTEMS COMPANY, ATK ORDNACE AND GROUND SYSTEMS LLC, ATK PRECISION SYSTEMS LLC, ATK TECTICAL SYSTEMS COMPANY LLC, ATKINTERNATIONAL SALES INC., COMPOSITE OPTICS, INCORPORTED, FEDERAL CARTRIDGE COMPANY, GASL, INC., MICRO CRAFT INC., MISSION RESEARCH CORPORATION, NEW RIVER ENERGETICS, INC., THIOKOL TECHNOGIES INTERNATIONAL, INC.
Assigned to BANK OF AMERICA, N.A. reassignment BANK OF AMERICA, N.A. SECURITY AGREEMENT Assignors: ALLIANT TECHSYSTEMS INC., AMMUNITION ACCESSORIES INC., ATK COMMERCIAL AMMUNITION COMPANY INC., ATK COMMERCIAL AMMUNITION HOLDINGS COMPANY, ATK LAUNCH SYSTEMS INC., ATK SPACE SYSTEMS INC., EAGLE INDUSTRIES UNLIMITED, INC., EAGLE MAYAGUEZ, LLC, EAGLE NEW BEDFORD, INC., FEDERAL CARTRIDGE COMPANY
Anticipated expiration legal-status Critical
Assigned to FEDERAL CARTRIDGE CO., COMPOSITE OPTICS, INC., ALLIANT TECHSYSTEMS INC., ORBITAL ATK, INC. (F/K/A ALLIANT TECHSYSTEMS INC.) reassignment FEDERAL CARTRIDGE CO. RELEASE BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: BANK OF AMERICA, N.A.
Assigned to FEDERAL CARTRIDGE CO., ALLIANT TECHSYSTEMS INC., EAGLE INDUSTRIES UNLIMITED, INC., AMMUNITION ACCESSORIES, INC., ORBITAL ATK, INC. (F/K/A ALLIANT TECHSYSTEMS INC.) reassignment FEDERAL CARTRIDGE CO. RELEASE BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: BANK OF AMERICA, N.A.
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
    • C06B45/12—Compositions or products which are defined by structure or arrangement of component of product having contiguous layers or zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges
    • F02K9/14—Shape or structure of solid propellant charges made from sheet-like materials, e.g. of carpet-roll type, of layered structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/16—Cartridges, i.e. cases with charge and missile characterised by composition or physical dimensions or form of propellant charge, with or without projectile, or powder
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/38—Separately-loaded propellant charges, e.g. cartridge bags

Definitions

  • This invention relates generally to ejectable projectiles and propellants for ejecting those projectiles from casings within which they are disposed. Specifically, this invention is directed to solid propellant systems for generating gases which eject projectiles from canisters or casings at a controlled velocity.
  • Projectiles such as rockets, missiles, and the like, are well-known in the aerospace and military industries. Propellants which are associated with such projectiles are also well-known. Some projectiles, such as rockets or missiles, typically comprise a warhead and an internal motor for urging the projectile forward to its target. Internal motors for driving the projectile may be of a solid propellant type, a liquid propellant type, or some other type known to those skilled in the art. Frequently, rockets, missiles, and similar projectiles are disposed within a closed-end casing or canister prior to firing. When fired, projectiles of this type must first be ejected from the canister. Projectiles which have an internal motor, i.e.
  • rockets must first be ejected from the canister before the rocket motor is ignited to prevent damage to the canister.
  • Solid propellant grains generally take many forms. For example, some propellants are poured into the rocket casing to fill a substantial percentage of it. Other propellant grains take the form of a carpet roll which is placed in the rocket casing end-to-end. Examples of such propellants are disclosed in U.S. Pat. No. 3,763,787 to Schultz, issued Oct. 9, 1973, and U.S. Pat. No. 3,737,348 to Schultz, issued Jun. 5, 1973, both of which disclose a double base propellant applied to both sides of a reinforcing material and rolled into a carpet-type roll. The reinforcing material provides a space between the propellant surfaces sufficient to provide a very large area of combustion.
  • the roll is placed within a rocket motor casing so that the roll is in a cross-sectional orientation to the casing.
  • the carpet roll is bonded to the inner casing of the rocket motor and is attached by adhesive means to a head plate.
  • propellant grain configurations are typically designed to provide a geometrically increasing surface area of propellant for burning. That is, as the exposed surface of the propellant burns, it exposes an ever increasing surface area for burning, and the resulting generation of gas from the burning propellant increases geometrically.
  • a propellant system for use in a class of projectiles which are disposed within an outer casing or canister and which are ejectable from the canister.
  • the propellant system of the invention provides a configured propellant grain, the burn surface of which is dependent upon the acceleration rate of the projectile with which it is associated. That is, the gas generated by the burning propellant is a function of the rate at which the ejectable projectile is displaced from the canister.
  • the propellant system of the present invention is configured to provide a surface area which is mechanically exposed for combustion by displacement of the exiting projectile. That is, the surface of the propellant is burned at a rate which is directly related to the rocket displacement.
  • the propellant system of the present invention provides a rapid-burning propellant grain which generates enough gas pressure within the canister to eject the rocket quickly from the canister yet without over pressurizing the canister.
  • the ejection acceleration as a function of pressure will generally differ.
  • the gas generation system of this invention compensates for such differences, controlling the canister pressure regardless of the particular projectile which is ejected.
  • the propellant gas-generation system of the invention generally comprises a propellant adhered to a non-burning substrate.
  • the propellant and substrate take the general form of a strip having a specific width and length.
  • the strip is then adhesively attached to itself in a manner which conceals part of the propellant and which will allow the strip to peel progressively and continuously from itself to expose concealed propellant for burning.
  • the substrate is a flexible material such as rubber which is not combustible in this application.
  • the propellant is joined to the substrate using a tenacious adhesive with a relatively high peel strength. Peel strength is defined as the pounds per linear inch (pli) required to separate one surface from another at a particular angle.
  • the strip of combined propellant and substrate is then attached to itself to form a relatively weak joint.
  • the adhesive used to join the strip of combined propellant and substrate to itself has a lower peel strength than the adhesive binding the propellant to the substrate. Consequently, the weaker peel strength adhesive will allow peeling of the strip from itself while the stronger peel strength will prevent peeling of the propellant from the substrate during detachment of the strip from itself.
  • the gas-generation system of the present invention is directed in one embodiment to the ejection of rockets which are slidably disposed within an outer casing or canister.
  • One end of the propellant/substrate strip is connected to the rocket, e.g. to the rear end of the rocket.
  • the other end of the propellant/substrate strip is connected in some manner to the closed end of the canister.
  • One end of the propellant/substrate strip is provided to expose a portion of the propellant.
  • Means for igniting the exposed propellant is provided within the canister, such as a pyrogen or pyrotechnic igniter which directs hot gases on the exposed surface.
  • the gas-producing units are easily constructed and provide an inexpenseive means for ejecting projectiles from a canister.
  • the pressure curve is easily tailored for each application by varying the propellant strip dimensions, mass and type of propellant, and other factors. A high batch-to-batch uniformity is readily maintained.
  • the propellant system of the present invention is also directed to use in ejecting non-motorized projectiles such as bombs, bomblets, submunitions, flares, chaff and the like, as well as such munitions as torpedoes from seagoing vessels.
  • non-motorized projectiles such as bombs, bomblets, submunitions, flares, chaff and the like, as well as such munitions as torpedoes from seagoing vessels.
  • FIG. 1 is a perspective view of the outer surface of a partially detached propellant gas-generation system of the invention
  • FIG. 3 is a partially fragmentary perspective view of the propellant system installed within a canister
  • FIG. 4 is a perspective view of the inner surface of a partially detached propellant gas-generation system
  • FIG. 5 is a perspective view of another embodiment of the outer surface of a partially detached propellant gas-generation system of the invention.
  • FIG. 6 is a perspective view of a further embodiment of the invention.
  • the substrate 12 of the propellant strip 16 is preferably a resilient material such as rubber but may be constructed of any suitable material which will adhere to the propellant 14 and which will allow the propellant strip 16 to be formed into any desired shape.
  • the maximum strain capacity (EM) is defined by the equation ##EQU1## where D o is the diameter of the rolled propellant strip measured from its outer circumference, and D i is the diameter of the rolled propellant strip measured from its inner circumference at the center of the roll.
  • D o is the diameter of the rolled propellant strip measured from its outer circumference
  • D i is the diameter of the rolled propellant strip measured from its inner circumference at the center of the roll.
  • a particularly suitable adhesive for tenaciously attaching the propellant to the substrate is TI-H-300, an adhesive manufactured by Thiokol Corporation (Elkton, MD), the ingredients of which include carboxy-terminated polybutadiene (CTPB), trifunctional epoxy liquid, chromium octoate, and carbon black.
  • CTPB carboxy-terminated polybutadiene
  • Any flexible adhesive which effects a bond between the propellant and the substrate and which has a relatively stronger peel strength as compared to the adhesive used to join the propellant strip together (described below) is suitable for use in the invention.
  • the propellant strip 16 is attached to itself in a manner which conceals propellant within the configured strip and which allows uniform and continuously progressive exposure of the concealed propellant 14 as the propellant strip is peeled from itself.
  • the propellant strip 16 may be rolled in carpet-roll fashion.
  • the outer surface 18 of the substrate 12 is continuously and progressively exposed, generally in the area designated 20, thereby exposing more and more of the propellant 14 as the unrolling continues.
  • the opposing edges of the propellant strip 16 are coated with a sealant 17 for deterring combustion from those edges.
  • a sealant 17 for deterring combustion from those edges.
  • the propellant 14 may preferably, in some cases, be applied on a grain of varying width and/or thickness to modify the gas-generation rate.
  • the propellant layer width 60 is decreased at point 62 to width 64 for reducing the gas-generation rate when the projectile is displaced distance 66.
  • the propellant dimension may be varied along the strip to achieve any desired pressure curve. This concept is more clearly understood by the discussion which follows.
  • One end 22 of the propellant strip 16 must be connected to the end of the rocket, and the other end 24 of the propellant strip 16 must be connected to the closed end of the outer casing or canister within which the rocket is disposed.
  • One method of connecting the propellant strip 16 to the canister is to wind one end 24 of the propellant strip 16 about a cylinder or mandrel 26. The mandrel 26 is then secured in some manner to the inside surface of the canister. As illustrated by FIG. 2, one means of securing the mandrel 26 to the inside surface of the outer casing is to attach the mandrel securely to a ring 28 using two rods 30 and 32 interconnected between the mandrel 26 and the ring 28. The ring is secured to the canister by bolt, screw, or other means.
  • FIG. 3 more fully illustrates the placement of the propellant strip 16 in the canister 34 within which the rocket 38 is disposed.
  • the free end 22 of the propellant strip 16 is attached to the bottom 40 of the rocket 38 so that when the rocket is ejected from the canister 36, it unrolls the propellant strip.
  • the attachment may be by a strong adhesive or other mechanical means.
  • the ring 28 is secured to the inside face of the bottom 42, i.e. closed end, of the canister 34.
  • the propellant strip 16 may be attached in any manner to the canister 34 as long as the propellant strip is able to peel away from itself or, as suggested by FIGS. 1-3, is able to be unrolled.
  • the propellant strip may be attached to itself in any configuration which provides the desired progressive exposure of the concealed propellant for burning as it is unrolled by the ejecting rocket.
  • the desired configuration must also be one which provides a first free end of the propellant strip for attachment to the rocket and a second free end of the propellant strip for attachment to the canister.
  • Such configurations include, for example, accordion folding or helical winding into a corkscrew shape.
  • Rolling, folding, or winding configurations as previously described provide a type of detachment of the strip which continuously exposes propellant for burning as the rocket is ejected from the canister.
  • the propellant strip is attached to itself by use of a weak adhesive (as compared to the relatively tenacious adhesive used to adhere the propellant to the substrate). As illustrated by FIG. 4, the weak adhesive 44 is applied to the inner facing surface 46 of the substrate 12. Any flexible adhesive may be used for joining the propellant strip together which is capable of maintaining the attachment of the propellant strip to itself (i.e., maintained in a roll) but which displays a sufficiently low peel strength to allow the attached propellant strip to peel away from itself (i.e., to unroll).
  • a particularly suitable adhesive for attaching the propellant strip to itself is TI-H-300 adhesive (described above) in admixture with Chemlok 234, an adhesive manufactured by Lord Corporation (Erie, PA).
  • TI-H-300 adhesive with Chemlok 234, an adhesive manufactured by Lord Corporation (Erie, PA).
  • Chemlok 234 adhesive produces an adhesive having an approximate four-fold decrease in peel strength as compared to TI-H-300 adhesive without Chemlok 234 adhesive.
  • the difference in peel strengths between the adhesive used to adhere the propellant to the substrate and the adhesive used to join the propellant strip together allows the propellant strip to peel away from itself without causing the propellant to dislodge from the substrate.
  • Both the weak and the strong adhesives should be resilient enough to avoid cracking when the propellant strip is attached to itself.
  • the TI-H-300 adhesive is also an excellent sealant for coating the lateral edges of the propellant strip 16 to deter combustion from those edges inwardly.
  • the exposed propellant ignites and burns down the length of the propellant strip until all of the exposed propellant has burned. Enough pressure is developed from the burning of the initially exposed propellant to urge the rocket or other projectile forward. As the rocket moves out of the casing, the forward motion of the rocket causes the propellant strip to detach from itself thereby exposing more propellant for burning. As the newly exposed propellant burns, gas is continuously produced to continuously increase the pressure which displaces the rocket from the canister. The detachment of the propellant strip continues until the propellant strip has been completely detached from itself, i.e. unwound, and all of the propellant has burned. The rocket is thus ejected from the canister and is separately fired and directed toward a target.
  • the mechanically controlled increasing surface area of exposed propellant provides smoothly increasing pressure within the casing as the propellant burns.
  • FIG. 6 depicts an exemplary configuration which is folded.
  • strip 70 includes a substrate 72 having ends 74 and 76 for attachment to the canister and to the ejectible, respectively.
  • a layer of propellant 78 overlies the substrate 72 and the combination folded into accordion pleats 80 to conceal a large portion of the propellant 78. As ends 74 and 76 are pulled apart, the pleats unfold to permit full combustion of the propellant.
  • strip 84 is wound similarly to that shown in FIG. 1, but the connections to the canister and the ejectible are on opposite sides 86 and 88 of the ends 90 and 92 of strip 84.
  • the roll detaches helically, like the common fly paper roll, to expose fresh propellant surface 94 for combustion.
  • the free end 22 of the strip 16 may be connected to the rocket through a series of pulleys which increases the velocity of the strip relative to the rocket.
  • a higher velocity may be required to prevent the propellant from extinguishing with slowly ejected projectiles.
  • the required velocity of unrolling or unfolding is a function of the propellant burn rate and propellant thickness.
  • Lower unrolling/unfolding velocities may be used with propellants of greater thickness and/or lower burn rate.
  • Propellants having a high burn rate and applied in a thin layer, e.g. 0.1 cm may require unrolling velocities as high as 6-8 meters/sec. or more to prevent extinguishment.
  • the particular dimensions of the propellant strip are dependent upon many factors. Among those factors are the size, shape and weight of the rocket, the size of the canister, and the type of propellant being used.
  • the pressurization curve is readily calculated for any projectile and propellant strip configuration.
  • the apparatus of the invention may be used to eject a wide variety of objects from a casing or canister. Thus, for example, the invention is useful for ejecting objects from aircraft, seagoing vessels, and stationary sites.
  • the invention provides a reliable gas generation which is adaptable to the ejection of any sized object from a canister.
  • the apparatus is easily and inexpensively constructed.
  • the ejection pressure may be pre-controlled to any desired time function.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Organic Chemistry (AREA)
  • Adhesives Or Adhesive Processes (AREA)
  • Toys (AREA)
US07/679,305 1991-04-02 1991-04-02 Propellant gas-generation system for canister ejection Expired - Lifetime US5363768A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US07/679,305 US5363768A (en) 1991-04-02 1991-04-02 Propellant gas-generation system for canister ejection
GB9205951A GB2307031B (en) 1991-04-02 1992-03-19 Propellant gas-generation system for canister ejection
FR9203940A FR2737288A1 (fr) 1991-04-02 1992-04-01 Systeme de generation d'un gaz propulseur pour ejecter un projectile d'un tube ferme a une extremite
US07/911,941 US5616884A (en) 1991-04-02 1992-07-10 Propellant gas-generation system for canister ejection

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/679,305 US5363768A (en) 1991-04-02 1991-04-02 Propellant gas-generation system for canister ejection

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US07/911,941 Continuation-In-Part US5616884A (en) 1991-04-02 1992-07-10 Propellant gas-generation system for canister ejection

Publications (1)

Publication Number Publication Date
US5363768A true US5363768A (en) 1994-11-15

Family

ID=24726388

Family Applications (1)

Application Number Title Priority Date Filing Date
US07/679,305 Expired - Lifetime US5363768A (en) 1991-04-02 1991-04-02 Propellant gas-generation system for canister ejection

Country Status (3)

Country Link
US (1) US5363768A (fr)
FR (1) FR2737288A1 (fr)
GB (1) GB2307031B (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140109755A1 (en) * 2009-02-11 2014-04-24 Saab Ab Decoy material package, a dispenser and a method for dispensing decoy material
CN103896694A (zh) * 2014-03-21 2014-07-02 西安近代化学研究所 防药条粘结装置及药条加工方法
US20200232772A1 (en) * 2019-01-21 2020-07-23 Spectre Materials Sciences, Inc. Propellant With Pattern-Controlled Burn Rate
US11650037B2 (en) 2021-02-16 2023-05-16 Spectre Materials Sciences, Inc. Primer for firearms and other munitions

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US751386A (en) * 1904-02-02 Cleland davis
US2743580A (en) * 1952-10-07 1956-05-01 Hughes Aircraft Co Igniter for rocket motors
US3176618A (en) * 1961-06-14 1965-04-06 Hexcel Products Inc Rocket motor construction and fabrication process
US3496870A (en) * 1967-05-23 1970-02-24 Us Navy Spiral burning propellant charge
US3737348A (en) * 1970-12-29 1973-06-05 Us Army Headend suspension for a carpet roll solid propellant grain
US3763787A (en) * 1971-02-11 1973-10-09 Us Army Carpet roll reinforced propellant and method for making
US3855176A (en) * 1970-02-16 1974-12-17 Us Navy Liner composition for rocket motors comprising crosslinked carboxy terminated polybutadiene with inert filler
DE2633652A1 (de) * 1976-07-27 1978-02-02 Bayern Chemie Gmbh Flugchemie Inhibierung fuer treibsaetze
US4615270A (en) * 1985-03-18 1986-10-07 Morton Thiokol, Inc. Printed sheet urethane propellant
US4792423A (en) * 1987-07-13 1988-12-20 United Technologies Corporation Method for making solid rocket propellant

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1270790B (de) * 1959-03-20 1968-06-20 H I Thompson Fiber Glass Co Kunstharzgebundener Faserstoffschichtbauteil
US3159104A (en) * 1959-11-02 1964-12-01 Solid Fuels Corp Laminated tape propellants
US3995559A (en) * 1962-06-21 1976-12-07 E. I. Du Pont De Nemours And Company Propellant grain with alternating layers of encapsulated fuel and oxidizer
DE1808111A1 (de) * 1968-11-09 1970-06-11 Dynamit Nobel Ag Feststofftreibsatz mit kurzer Brennzeit fuer Raketentriebwerke
US4013743A (en) * 1973-02-12 1977-03-22 Rockwell International Corporation Spiral grain solid propellant fabrication process
US4275657A (en) * 1976-12-30 1981-06-30 Societe Nationale Des Poudres Et Explosifs Spirally wound pyrotechnic charge useful for the propulsion of an engine and the like
DE3630083A1 (de) * 1986-09-04 1988-03-10 Bayern Chemie Gmbh Flugchemie Vorrichtung zum ausstossen von behaeltern, insbesondere von munition

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US751386A (en) * 1904-02-02 Cleland davis
US2743580A (en) * 1952-10-07 1956-05-01 Hughes Aircraft Co Igniter for rocket motors
US3176618A (en) * 1961-06-14 1965-04-06 Hexcel Products Inc Rocket motor construction and fabrication process
US3496870A (en) * 1967-05-23 1970-02-24 Us Navy Spiral burning propellant charge
US3855176A (en) * 1970-02-16 1974-12-17 Us Navy Liner composition for rocket motors comprising crosslinked carboxy terminated polybutadiene with inert filler
US3737348A (en) * 1970-12-29 1973-06-05 Us Army Headend suspension for a carpet roll solid propellant grain
US3763787A (en) * 1971-02-11 1973-10-09 Us Army Carpet roll reinforced propellant and method for making
DE2633652A1 (de) * 1976-07-27 1978-02-02 Bayern Chemie Gmbh Flugchemie Inhibierung fuer treibsaetze
US4615270A (en) * 1985-03-18 1986-10-07 Morton Thiokol, Inc. Printed sheet urethane propellant
US4792423A (en) * 1987-07-13 1988-12-20 United Technologies Corporation Method for making solid rocket propellant

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140109755A1 (en) * 2009-02-11 2014-04-24 Saab Ab Decoy material package, a dispenser and a method for dispensing decoy material
CN103896694A (zh) * 2014-03-21 2014-07-02 西安近代化学研究所 防药条粘结装置及药条加工方法
US20200232772A1 (en) * 2019-01-21 2020-07-23 Spectre Materials Sciences, Inc. Propellant With Pattern-Controlled Burn Rate
US11112222B2 (en) * 2019-01-21 2021-09-07 Spectre Materials Sciences, Inc. Propellant with pattern-controlled burn rate
US11650037B2 (en) 2021-02-16 2023-05-16 Spectre Materials Sciences, Inc. Primer for firearms and other munitions

Also Published As

Publication number Publication date
GB2307031A (en) 1997-05-14
FR2737288A1 (fr) 1997-01-31
GB2307031B (en) 1998-01-07
GB9205951D0 (en) 1996-12-04

Similar Documents

Publication Publication Date Title
US5675966A (en) Solid propellant dual pulse rocket motor loaded case and ignition system and method of manufacture
US4944226A (en) Expandable telescoped missile airframe
EP2342444B1 (fr) Moteur-fusée insensible
US9605932B2 (en) Gas generators, launch tubes including gas generators and related systems and methods
EP0526835A1 (fr) Douille combustible multi-couche
US6352030B1 (en) Gas generating eject motor
US20040050282A1 (en) Rocket motors with insensitive munitions systems and projectiles including same
US3177809A (en) Semi-fixed artillery round
US3026772A (en) Cargo launcher
US5616884A (en) Propellant gas-generation system for canister ejection
JP2004526937A (ja) 火器用の管状弾丸を有する銃身アセンブリ
US5363768A (en) Propellant gas-generation system for canister ejection
KR20030009485A (ko) 일시적인 공중영상 형성방법
US4154141A (en) Ultrafast, linearly-deflagration ignition system
US5423264A (en) Firework bomb with integral combustion
EP0475279B1 (fr) Revêtement d'allumage dans une charge propulsive principale d'une munition téléscopique
US6481198B1 (en) Multi-stage rocket motor assembly including jettisonable launch motor integrated with flight igniter
CA2062143A1 (fr) Systeme propulsif a generation de gaz pour ejection d'un contenant
US9121668B1 (en) Aerial vehicle with combustible time-delay fuse
US3983818A (en) Incendiary tracer projectile
JPH0370996A (ja) ガス発生器ミサイル発射システム
US4930420A (en) Seal for the nozzle opening of a projectile
US3886841A (en) Rocket powered round
US4170875A (en) Caseless rocket design
US10281248B2 (en) Gas generators, launch tube assemblies including gas generators, and related systems and methods

Legal Events

Date Code Title Description
AS Assignment

Owner name: THIOKOL CORPORATION, 2475 WASHINGTON BLVD., OGDEN,

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNORS:SOLBERG, MARK A.;HARTWELL, JAMES A.;REEL/FRAME:005672/0963

Effective date: 19910320

STCF Information on status: patent grant

Free format text: PATENTED CASE

FPAY Fee payment

Year of fee payment: 4

AS Assignment

Owner name: CORDANT TECHNOLOGIES, INC., UTAH

Free format text: CHANGE OF NAME;ASSIGNOR:THIOKOL CORPORATION;REEL/FRAME:011712/0322

Effective date: 19980423

AS Assignment

Owner name: THE CHASE MANHATTAN BANK, NEW YORK

Free format text: PATENT SECURITY AGREEMENT;ASSIGNOR:ALLIANT TECHSYSTEMS INC.;REEL/FRAME:011821/0001

Effective date: 20010420

AS Assignment

Owner name: ALLIANT TECHSYSTEMS INC., MINNESOTA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:THIOKOL PROPULSION CORP.;REEL/FRAME:012343/0001

Effective date: 20010907

Owner name: THIOKOL PROPULSION CORP., UTAH

Free format text: CHANGE OF NAME;ASSIGNOR:CORDANT TECHNOLOGIES INC.;REEL/FRAME:012391/0001

Effective date: 20010420

FPAY Fee payment

Year of fee payment: 8

AS Assignment

Owner name: ALLIANT TECHSYSTEMS INC., MINNESOTA

Free format text: RELEASE OF SECURITY AGREEMENT;ASSIGNOR:JPMORGAN CHASE BANK (FORMERLY KNOWN AS THE CHASE MANHATTAN BANK);REEL/FRAME:015201/0095

Effective date: 20040331

AS Assignment

Owner name: BANK OF AMERICA, N.A., NORTH CAROLINA

Free format text: SECURITY INTEREST;ASSIGNORS:ALLIANT TECHSYSTEMS INC.;ALLANT AMMUNITION AND POWDER COMPANY LLC;ALLIANT AMMUNITION SYSTEMS COMPANY LLC;AND OTHERS;REEL/FRAME:014692/0653

Effective date: 20040331

FPAY Fee payment

Year of fee payment: 12

AS Assignment

Owner name: BANK OF AMERICA, N.A., CALIFORNIA

Free format text: SECURITY AGREEMENT;ASSIGNORS:ALLIANT TECHSYSTEMS INC.;AMMUNITION ACCESSORIES INC.;ATK COMMERCIAL AMMUNITION COMPANY INC.;AND OTHERS;REEL/FRAME:025321/0291

Effective date: 20101007

AS Assignment

Owner name: ORBITAL ATK, INC. (F/K/A ALLIANT TECHSYSTEMS INC.)

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:BANK OF AMERICA, N.A.;REEL/FRAME:036815/0330

Effective date: 20150929

Owner name: COMPOSITE OPTICS, INC., CALIFORNIA

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:BANK OF AMERICA, N.A.;REEL/FRAME:036815/0330

Effective date: 20150929

Owner name: ALLIANT TECHSYSTEMS INC., VIRGINIA

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:BANK OF AMERICA, N.A.;REEL/FRAME:036815/0330

Effective date: 20150929

Owner name: FEDERAL CARTRIDGE CO., MINNESOTA

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:BANK OF AMERICA, N.A.;REEL/FRAME:036815/0330

Effective date: 20150929

AS Assignment

Owner name: ORBITAL ATK, INC. (F/K/A ALLIANT TECHSYSTEMS INC.), VIRGINIA

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:BANK OF AMERICA, N.A.;REEL/FRAME:036816/0624

Effective date: 20150929

Owner name: EAGLE INDUSTRIES UNLIMITED, INC., MISSOURI

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:BANK OF AMERICA, N.A.;REEL/FRAME:036816/0624

Effective date: 20150929

Owner name: ALLIANT TECHSYSTEMS INC., VIRGINIA

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:BANK OF AMERICA, N.A.;REEL/FRAME:036816/0624

Effective date: 20150929

Owner name: AMMUNITION ACCESSORIES, INC., ALABAMA

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:BANK OF AMERICA, N.A.;REEL/FRAME:036816/0624

Effective date: 20150929

Owner name: FEDERAL CARTRIDGE CO., MINNESOTA

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:BANK OF AMERICA, N.A.;REEL/FRAME:036816/0624

Effective date: 20150929

Owner name: ORBITAL ATK, INC. (F/K/A ALLIANT TECHSYSTEMS INC.)

Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:BANK OF AMERICA, N.A.;REEL/FRAME:036816/0624

Effective date: 20150929